串置翼型数值模拟及气动特性分析  

Numerical Simulations of Tandem-Airfoil

作　　者：李广佳[1] 李锋[1] 石文[1] 

机构地区：[1]航天空气动力技术研究院,北京100074

出　　处：《飞机设计》2006年第1期19-24,共6页Aircraft Design

摘　　要：串置机翼构型研究自从19世纪70年代之后已经成为航空领域的一个研究焦点。研究人员发现,此种布局构型除了结构和质量方面的优势,在理论上通过改变2个机翼之间的升力分布可以使得飞机的诱导阻力有较大减少。这种非常规布局为未来飞机设计提供了一个很好的选择。本文采用二维RANS方程求解器并结合S-A湍流模型对串置翼型在±6°翼差角的不同水平相对距离组合位置进行了数值模拟计算。计算结果表明,在负的翼差角下,水平相对位置越远,串翼系统的升阻比越高;在正的翼差角下,较近的水平相对位置升阻比较高。Studies of tandem wing configurations have received considerable attention in the aerospace community since the early 1970＇ s. In addition to advantages in structure and weight, this configuration can theoretically provides 50% reduction of induced drag through varying the lift distribution between the two wings. Therefore, the unconventional configuration provides an option for future aircraft designs. A numerical simulation for a tandem-airfoil configuration was performed for different staggers at ±6°decalages using the two-dimensional RANTS equation solver, combined with the S-A vortex model. The simulation results indicated that the ger at the positive decalage and decreased with lift-to-drag ratio is increased with increase of the stagincrease of the stagger at the negative decalage .

关 键 词：串置机翼构型 数值模拟 升阻比 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]